US20070224559A1 - Combustion Chamber - Google Patents
Combustion Chamber Download PDFInfo
- Publication number
- US20070224559A1 US20070224559A1 US11/676,584 US67658407A US2007224559A1 US 20070224559 A1 US20070224559 A1 US 20070224559A1 US 67658407 A US67658407 A US 67658407A US 2007224559 A1 US2007224559 A1 US 2007224559A1
- Authority
- US
- United States
- Prior art keywords
- burner
- fuel
- combustion chamber
- burners
- computing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N1/00—Regulating fuel supply
- F23N1/002—Regulating fuel supply using electronic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
- F23N5/08—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements
- F23N5/082—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements using electronic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/16—Systems for controlling combustion using noise-sensitive detectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2223/00—Signal processing; Details thereof
- F23N2223/10—Correlation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2225/00—Measuring
- F23N2225/04—Measuring pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2231/00—Fail safe
- F23N2231/06—Fail safe for flame failures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2237/00—Controlling
- F23N2237/02—Controlling two or more burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
- F23N5/08—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements
Definitions
- the invention relates to a combustion chamber, in particular to one in a gas turbine, having at least two burners that are connected to a fuel supply via controllable fuel valves.
- Gas turbines are used, for example, for the generation of electrical energy in power plants, where they drive generators. Such turbines usually have a power of more than 50 MW and are designed, in particular, for stationary continuous operation. In order to be able to operate the gas turbine economically and with low pollutant emissions, in particular NO x , the aim should be to operate it in a lean fashion, that is to say with as little fuel as possible, and, on the other hand, to avoid extinguishing the burner, since restarting the gas turbine is complicated and expensive.
- Pulsation of the flame depends in this case on various parameters such as, for example, an air volumetric flow and a fuel volumetric flow associated therewith, as well as on a fuel chamber temperature.
- One of numerous aspect of the present invention is concerned with the problem in the case of a combustion chamber of a gas turbine of the aforementioned type mentioned, of detecting pulsation-prone burners as early as possible and, if appropriate, of taking suitable countermeasures such that a pulsation-free operation of the combustion chamber can be ensured.
- Another aspect of the present invention involves the general idea of providing measuring devices that are suitable in the case of a combustion chamber, in particular of a combustion chamber of a gas turbine, with a number of burners and which determine burner-specific data from which a computing and control device can calculate correlation values that permit the burners to be divided into pulsation-prone and non-pulsation-prone burners. If the computing and control device specifies a burner as pulsation-prone on the basis of the values measured in the combustion chamber, more fuel is fed to this burner and the risk of pulsation is thereby reduced.
- the detection of the data of the combustion chamber for judging whether a burner is a critical one, that is to say prone to pulsation, is performed on the one hand via an optical measuring device that is assigned to each burner and is designed for detecting chemiluminescent radiation and, on the other hand, via a further measuring device in the form of a pressure sensor for detecting a combustion chamber pressure.
- the burners themselves are connected to a fuel supply via controllable fuel valves.
- the computing and control device is connected to them on the input side. On the output side, the computing and control device is connected to the controllable fuel valves, and this enables at least the burners prone to pulsation to be controlled via a changed fuel feed.
- the computing and control device is designed, furthermore, in such a way that it calculates a correlation from the chemiluminescent radiation values and the pressures, and determines the burner or a burner group with the highest correlation.
- the associated fuel valve(s) of the burners thereby determined are thereupon opened by the computing and control device and the pulsation tendency of the burners is thereby reduced.
- the combustion chamber according to the invention can therefore be used for early detection of burners prone to pulsation, that is to say critical burners, and to take suitable countermeasures. This permits an overall lean operation of the combustion chamber and therefore low emission values, it being possible at the same time effectively to exclude an extinction of the flame in the combustion chamber. This firstly increases the efficiency, and secondly the cost effectiveness of the gas turbine equipped with the combustion chamber according to the invention.
- the optical measuring devices and/or the pressure sensor and/or the fuel valves prefferably be connected to the computing and control device in a communicating fashion via a BUS, such as a CAN BUS.
- a BUS such as a CAN BUS.
- Such CAN BUS systems enable a comprehensive data exchange and a corresponding communication between the different components that are connected and mutually networked.
- CAN BUS systems create far reaching networking possibilities such that it is also conceivable to be able to connect further units for measuring, detecting or processing data, and to connect devices designed for controlling specific parameters.
- the optical measuring devices each have an optical fiber.
- the space requirement of such an optical fiber in the combustion chamber is minimal, for which reason it can also be installed at sites offering little space.
- a sensor system of the optical measuring device is not exposed directly to the high temperatures prevailing in the combustion chamber, and this has a positive effect on the service life of the optical measuring devices.
- FIGURE shows a highly schematic illustration of a combustion chamber according to the invention with associated computing and control device.
- a highly schematic combustion chamber 1 for example as used in a gas turbine, has a number of burners A to H that are connected via controllable fuel valves 2 to a fuel supply 3 , for example a fuel line.
- the number of the burners A to H here eight, is to be understood as purely exemplary, and so the invention is also intended to comprise a fuel chamber 1 with more than eight or less than eight, but at least two burners.
- the burners A to H are arranged, for example, in an annular fashion and each have at least one optical measuring device 4 for detecting chemiluminescent radiation, in particular for detecting an OH chemiluminescence.
- the optical measuring devices 4 are connected to a computing and control device 6 via corresponding signal lines 5 , in particular via a CAN bus 8 .
- the fuel valves 2 , 2 ′ can also be connected to the computing and control device 6 via corresponding control lines 5 ′′ via the CAN BUS 8 .
- the optical measuring devices 4 detect light produced in the combustion chamber 1 because of chemical reactions, and, in accordance with a preferred embodiment, have an optical fiber.
- the optical fiber is responsible in this case for guiding light between the burner and the actual optical measuring device.
- Such an optical fiber can be, for example, a glass fiber that guides light signals from the burner to the optical measuring device 4 .
- This offers the advantages that the optical measuring device 4 itself need not be arranged directly at the burner and is thereby exposed only to a substantially reduced temperature stress, and a requisite space requirement for the optical fiber is substantially less than for the optical measuring device 4 , such that the latter can be arranged at virtually any desired site in the vicinity of the burner given little space on offer.
- a pressure sensor 7 for detecting a pressure is arranged in the combustion chamber 1 and likewise connected to an input side of the computing and control device 6 via a corresponding signal line 5 ′.
- the pressure sensors can optionally also be connected to the computing and control device 6 via the CAN bus 8 .
- the computing and control device 6 is now designed in such a way that it calculates a correlation between the chemiluminescent radiation of each burner A to H and the pressure in the combustion chamber 1 from the measured values incoming from the optical measuring devices 4 and the pressure sensor 7 .
- the computing and control device 6 is connected to the fuel valves 2 associated with each of the burners A to H.
- the computing and control device 6 is designed in such a way that it determines the burner or a burner group with the highest correlation between chemiluminescent radiation and combustion chamber pressure, and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group.
- the computing and control device 6 opens the respectively associated fuel valve.
- a high correlation between the optical measured values and the combustion chamber pressure indicates, in this case, a pulsation tendency of the respective burner that is to be reduced in accordance with principles of the present invention.
- Pulsation-prone burners can therefore be identified by a high correlation between chemiluminescent radiation values and pressure values in the combustion chamber 1 . It is conceivable here that the computing and control device 6 control only a single burner with the respectively highest correlation value by opening the associated fuel valve, or else an entire group of burners whose respective correlation values lie above a limiting value.
- the combination to form a burner group can either comprise, for example, the burners A and B if these two have the two highest correlation values, or the burners can already be combined in advance to form specific groups, for example to form A, C, E and G such that the latter are controlled as a whole when only one of the said burners exceeds the correlation limiting value.
- the computing and/or control device 6 In order for the gas turbine not to overheat, when one or more fuel valves 2 are opened the others are proportionately throttled such that a substantially constant combustion chamber temperature or a substantially constant fuel flow can be maintained. In the case of a control operation by the computing and/or control device 6 , more fuel is therefore fed to the pulsation-prone burners and, at the same time, less fuel is fed to the non-pulsation-prone burners.
- the computing and control device 6 can open the fuel valves only starting from a specific predefined correlation value, and so no control is exercised given a correlation for which there is no pulsation tendency yet. It goes without saying that the computing and control device 6 countercontrols the fuel valves of the non-pulsation-prone burners only if no pulsation occurs in their case.
- the measuring device 4 assigned respectively to a burner detects chemiluminescent radiation, for example an OH radical radiation, while a pressure sensor 7 simultaneously determines the pressure in the combustion chamber 1 .
- the measured data determined in such a way are transmitted via lines 5 , 5 ′, for example via a CAN bus 8 , to the computing and control device 6 which calculates a correlation therefrom. If the calculated correlation value exceeds a predefined correlation limiting value, the computing and control device 6 opens the associated fuel valve(s) and thereby reduces the risk of pulsation of the associated burner or the associated burner group.
- the computing and control device 6 reduces the fuel feed to the other, non-pulsation-prone burners, that is to say those burners whose correlation value is below the correlation limiting value, such that a substantially constant combustion chamber temperature or a substantially constant fuel flow is preferably maintained.
- the computing and control device 6 counter-controls the fuel valves of the non-pulsation-prone burners only if in the case of the latter no risk of pulsation or no pulsation occurs.
Abstract
Description
- This application claims priority under 35 U.S.C. § 119 to German application number 10 2006 015 230.1, filed 30 Mar. 2006, the entirety of which is incorporated by reference herein.
- 1. Field of the Invention
- The invention relates to a combustion chamber, in particular to one in a gas turbine, having at least two burners that are connected to a fuel supply via controllable fuel valves.
- 2. Brief Description of the Related Art
- Gas turbines are used, for example, for the generation of electrical energy in power plants, where they drive generators. Such turbines usually have a power of more than 50 MW and are designed, in particular, for stationary continuous operation. In order to be able to operate the gas turbine economically and with low pollutant emissions, in particular NOx, the aim should be to operate it in a lean fashion, that is to say with as little fuel as possible, and, on the other hand, to avoid extinguishing the burner, since restarting the gas turbine is complicated and expensive.
- However, this can give rise to a conflict of aims, since it is possible, particularly in the case of a lean operation of the gas turbine, for the flame in the combustion chamber to pulsate, and this leads to extinction of the same in the most unfavorable case. Pulsation of the flame depends in this case on various parameters such as, for example, an air volumetric flow and a fuel volumetric flow associated therewith, as well as on a fuel chamber temperature. Fundamentally, what is desired for the burners or the combustion chamber is a flame system that can be designated as stable, and in the case of which a quasi-stationary pulsation-free ignition zone is formed in the vicinity of the burner outlet that, apart from turbulence-induced stochastic positional fluctuations, burns at a fixed location even in the event of slight fluctuations in the entry flows.
- For the purpose of being able to prevent pulsation of the flame in the combustion chamber, and thereby possible extinction of the flame, it is important to detect pulsation-prone burners as early as possible and to take appropriate countermeasures, since, as mentioned above, restarting the gas turbine because of an extinction of the flame is very complicated and expensive, and the economic efficiency of the gas turbine is negatively influenced thereby. Moreover, pulsating burners also diminish the efficiency of the gas turbine such that it should also be ensured with regard to a power yield that the quasi-stationary, pulsation-free ignition zone be formed in the region of the vicinity of the burner outlet.
- This is where principles of the invention come in. One of numerous aspect of the present invention is concerned with the problem in the case of a combustion chamber of a gas turbine of the aforementioned type mentioned, of detecting pulsation-prone burners as early as possible and, if appropriate, of taking suitable countermeasures such that a pulsation-free operation of the combustion chamber can be ensured.
- Another aspect of the present invention involves the general idea of providing measuring devices that are suitable in the case of a combustion chamber, in particular of a combustion chamber of a gas turbine, with a number of burners and which determine burner-specific data from which a computing and control device can calculate correlation values that permit the burners to be divided into pulsation-prone and non-pulsation-prone burners. If the computing and control device specifies a burner as pulsation-prone on the basis of the values measured in the combustion chamber, more fuel is fed to this burner and the risk of pulsation is thereby reduced. The detection of the data of the combustion chamber for judging whether a burner is a critical one, that is to say prone to pulsation, is performed on the one hand via an optical measuring device that is assigned to each burner and is designed for detecting chemiluminescent radiation and, on the other hand, via a further measuring device in the form of a pressure sensor for detecting a combustion chamber pressure. The burners themselves are connected to a fuel supply via controllable fuel valves. In order to process the data incoming from the optical measuring devices and the pressure sensor, the computing and control device is connected to them on the input side. On the output side, the computing and control device is connected to the controllable fuel valves, and this enables at least the burners prone to pulsation to be controlled via a changed fuel feed. The computing and control device is designed, furthermore, in such a way that it calculates a correlation from the chemiluminescent radiation values and the pressures, and determines the burner or a burner group with the highest correlation. The associated fuel valve(s) of the burners thereby determined are thereupon opened by the computing and control device and the pulsation tendency of the burners is thereby reduced. The combustion chamber according to the invention can therefore be used for early detection of burners prone to pulsation, that is to say critical burners, and to take suitable countermeasures. This permits an overall lean operation of the combustion chamber and therefore low emission values, it being possible at the same time effectively to exclude an extinction of the flame in the combustion chamber. This firstly increases the efficiency, and secondly the cost effectiveness of the gas turbine equipped with the combustion chamber according to the invention.
- It is expedient for the optical measuring devices and/or the pressure sensor and/or the fuel valves to be connected to the computing and control device in a communicating fashion via a BUS, such as a CAN BUS. Such CAN BUS systems enable a comprehensive data exchange and a corresponding communication between the different components that are connected and mutually networked. In particular, such CAN BUS systems create far reaching networking possibilities such that it is also conceivable to be able to connect further units for measuring, detecting or processing data, and to connect devices designed for controlling specific parameters.
- In a preferred embodiment of the solution according to the invention, the optical measuring devices each have an optical fiber. This offers the advantage that the optical measuring device need not be arranged directly in the combustion chamber, but needs to be connected to the combustion chamber only via such an optical fiber. Moreover, the space requirement of such an optical fiber in the combustion chamber is minimal, for which reason it can also be installed at sites offering little space. Moreover, a sensor system of the optical measuring device is not exposed directly to the high temperatures prevailing in the combustion chamber, and this has a positive effect on the service life of the optical measuring devices.
- Further important features and advantages of the invention follow from the drawing and from the associated description of the figures with the aid of the drawing.
- A preferred exemplary embodiment of the invention is illustrated in the drawing and explained in more detail in the following description.
- The sole FIGURE shows a highly schematic illustration of a combustion chamber according to the invention with associated computing and control device.
- In accordance with the drawing FIGURE, a highly
schematic combustion chamber 1, for example as used in a gas turbine, has a number of burners A to H that are connected viacontrollable fuel valves 2 to afuel supply 3, for example a fuel line. The number of the burners A to H, here eight, is to be understood as purely exemplary, and so the invention is also intended to comprise afuel chamber 1 with more than eight or less than eight, but at least two burners. - The burners A to H are arranged, for example, in an annular fashion and each have at least one
optical measuring device 4 for detecting chemiluminescent radiation, in particular for detecting an OH chemiluminescence. The opticalmeasuring devices 4 are connected to a computing andcontrol device 6 viacorresponding signal lines 5, in particular via aCAN bus 8. Moreover, thefuel valves control device 6 viacorresponding control lines 5″ via the CANBUS 8. Theoptical measuring devices 4 detect light produced in thecombustion chamber 1 because of chemical reactions, and, in accordance with a preferred embodiment, have an optical fiber. The optical fiber is responsible in this case for guiding light between the burner and the actual optical measuring device. Such an optical fiber can be, for example, a glass fiber that guides light signals from the burner to theoptical measuring device 4. This offers the advantages that theoptical measuring device 4 itself need not be arranged directly at the burner and is thereby exposed only to a substantially reduced temperature stress, and a requisite space requirement for the optical fiber is substantially less than for theoptical measuring device 4, such that the latter can be arranged at virtually any desired site in the vicinity of the burner given little space on offer. - Furthermore, a
pressure sensor 7 for detecting a pressure is arranged in thecombustion chamber 1 and likewise connected to an input side of the computing andcontrol device 6 via acorresponding signal line 5′. The pressure sensors can optionally also be connected to the computing andcontrol device 6 via the CANbus 8. According to the invention, the computing andcontrol device 6 is now designed in such a way that it calculates a correlation between the chemiluminescent radiation of each burner A to H and the pressure in thecombustion chamber 1 from the measured values incoming from theoptical measuring devices 4 and thepressure sensor 7. On the output side, the computing andcontrol device 6 is connected to thefuel valves 2 associated with each of the burners A to H. - Furthermore, the computing and
control device 6 is designed in such a way that it determines the burner or a burner group with the highest correlation between chemiluminescent radiation and combustion chamber pressure, and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group. Thus, once the correlation between the incoming optical measured values and the incoming combustion chamber pressure reaches a specific limiting value, the computing andcontrol device 6 opens the respectively associated fuel valve. A high correlation between the optical measured values and the combustion chamber pressure indicates, in this case, a pulsation tendency of the respective burner that is to be reduced in accordance with principles of the present invention. The pulsing of the flame firstly poses the risk of the latter's extinction, and there is secondly a reduction in the efficiency of the gas turbine. Pulsation-prone burners can therefore be identified by a high correlation between chemiluminescent radiation values and pressure values in thecombustion chamber 1. It is conceivable here that the computing andcontrol device 6 control only a single burner with the respectively highest correlation value by opening the associated fuel valve, or else an entire group of burners whose respective correlation values lie above a limiting value. - The combination to form a burner group can either comprise, for example, the burners A and B if these two have the two highest correlation values, or the burners can already be combined in advance to form specific groups, for example to form A, C, E and G such that the latter are controlled as a whole when only one of the said burners exceeds the correlation limiting value.
- In order for the gas turbine not to overheat, when one or
more fuel valves 2 are opened the others are proportionately throttled such that a substantially constant combustion chamber temperature or a substantially constant fuel flow can be maintained. In the case of a control operation by the computing and/orcontrol device 6, more fuel is therefore fed to the pulsation-prone burners and, at the same time, less fuel is fed to the non-pulsation-prone burners. Here, as explained above, the computing andcontrol device 6 can open the fuel valves only starting from a specific predefined correlation value, and so no control is exercised given a correlation for which there is no pulsation tendency yet. It goes without saying that the computing andcontrol device 6 countercontrols the fuel valves of the non-pulsation-prone burners only if no pulsation occurs in their case. - The aim below is to provide a brief explanation of a method according to the invention for controlling a combustion operation in the above described gas turbine:
- The measuring
device 4 assigned respectively to a burner detects chemiluminescent radiation, for example an OH radical radiation, while apressure sensor 7 simultaneously determines the pressure in thecombustion chamber 1. The measured data determined in such a way are transmitted vialines CAN bus 8, to the computing andcontrol device 6 which calculates a correlation therefrom. If the calculated correlation value exceeds a predefined correlation limiting value, the computing andcontrol device 6 opens the associated fuel valve(s) and thereby reduces the risk of pulsation of the associated burner or the associated burner group. At the same time, the computing andcontrol device 6 reduces the fuel feed to the other, non-pulsation-prone burners, that is to say those burners whose correlation value is below the correlation limiting value, such that a substantially constant combustion chamber temperature or a substantially constant fuel flow is preferably maintained. In general, the computing andcontrol device 6 counter-controls the fuel valves of the non-pulsation-prone burners only if in the case of the latter no risk of pulsation or no pulsation occurs.List of Reference Numerals 1 Combustion chamber 2 Fuel valve 3 Fuel supply/ fuel line 4 Optical measuring device 5 Lead/control line/ signal line 6 Computing and control device 7 Pressure sensor 8 CAN bus A-H Burners - While the invention has been described in detail with reference to exemplary embodiments thereof, it will be apparent to one skilled in the art that various changes can be made, and equivalents employed, without departing from the scope of the invention. The foregoing description of the preferred embodiments of the invention has been presented for purposes of illustration and description. It is not intended to be exhaustive or to limit the invention to the precise form disclosed, and modifications and variations are possible in light of the above teachings or may be acquired from practice of the invention. The embodiments were chosen and described in order to explain the principles of the invention and its practical application to enable one skilled in the art to utilize the invention in various embodiments as are suited to the particular use contemplated. It is intended that the scope of the invention be defined by the claims appended hereto, and their equivalents. The entirety of each of the aforementioned documents is incorporated by reference herein.
Claims (12)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006015230.1 | 2005-03-30 | ||
DE102006015230 | 2006-03-30 | ||
DE102006015230A DE102006015230A1 (en) | 2006-03-30 | 2006-03-30 | combustion chamber |
Publications (2)
Publication Number | Publication Date |
---|---|
US20070224559A1 true US20070224559A1 (en) | 2007-09-27 |
US7901203B2 US7901203B2 (en) | 2011-03-08 |
Family
ID=38197487
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/676,584 Expired - Fee Related US7901203B2 (en) | 2006-03-30 | 2007-02-20 | Combustion chamber |
Country Status (3)
Country | Link |
---|---|
US (1) | US7901203B2 (en) |
EP (1) | EP1840464B1 (en) |
DE (1) | DE102006015230A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2947389A1 (en) * | 2014-05-23 | 2015-11-25 | United Technologies Corporation | A gas turbine engine optical system |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
CN113915007A (en) * | 2021-11-11 | 2022-01-11 | 西安热工研究院有限公司 | Novel combustion pressure pulsation control system of gas turbine |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007016018A1 (en) * | 2007-04-03 | 2008-10-09 | Sms Demag Ag | burner arrangement |
DE102011117603A1 (en) | 2010-11-17 | 2012-05-24 | Alstom Technology Ltd. | Combustion chamber and method for damping pulsations |
DE102011118411A1 (en) * | 2010-12-09 | 2012-06-14 | Alstom Technology Ltd. | Combustion chamber and method for supplying fuel to a combustion chamber |
US9964455B2 (en) | 2014-10-02 | 2018-05-08 | General Electric Company | Methods for monitoring strain and temperature in a hot gas path component |
US9395301B2 (en) | 2014-10-02 | 2016-07-19 | General Electric Company | Methods for monitoring environmental barrier coatings |
EP3757460B1 (en) * | 2019-06-28 | 2022-06-22 | Ansaldo Energia Switzerland AG | Gas turbine engine with active protection from flame extinction and method of operating a gas turbine engine |
Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4913647A (en) * | 1986-03-19 | 1990-04-03 | Honeywell Inc. | Air fuel ratio control |
US4934926A (en) * | 1988-03-25 | 1990-06-19 | Agency Of Industrial Science & Technology, Ministry Of International Trade & Industry | Method and apparatus for monitoring and controlling burner operating air equivalence ratio |
US5249954A (en) * | 1992-07-07 | 1993-10-05 | Electric Power Research Institute, Inc. | Integrated imaging sensor/neural network controller for combustion systems |
US5487266A (en) * | 1992-05-05 | 1996-01-30 | General Electric Company | Combustion control for producing low NOx emissions through use of flame spectroscopy |
US5522721A (en) * | 1993-10-29 | 1996-06-04 | L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Process for combustion in an industrial furnace |
US5544478A (en) * | 1994-11-15 | 1996-08-13 | General Electric Company | Optical sensing of combustion dynamics |
US5706643A (en) * | 1995-11-14 | 1998-01-13 | United Technologies Corporation | Active gas turbine combustion control to minimize nitrous oxide emissions |
US5755819A (en) * | 1996-05-24 | 1998-05-26 | General Electric Company | Photodiode array for analysis of multi-burner gas combustors |
US5978525A (en) * | 1996-06-24 | 1999-11-02 | General Electric Company | Fiber optic sensors for gas turbine control |
US6464489B1 (en) * | 1997-11-24 | 2002-10-15 | Alstom | Method and apparatus for controlling thermoacoustic vibrations in a combustion system |
US6468069B2 (en) * | 1999-10-25 | 2002-10-22 | Jerome H. Lemelson | Automatically optimized combustion control |
US6702571B2 (en) * | 2001-09-05 | 2004-03-09 | Gas Technology Institute | Flex-flame burner and self-optimizing combustion system |
US6742341B2 (en) * | 2002-07-16 | 2004-06-01 | Siemens Westinghouse Power Corporation | Automatic combustion control for a gas turbine |
US20050247064A1 (en) * | 2004-02-06 | 2005-11-10 | Lieuwen Tim C | Systems and methods for detection of combustor stability margin |
US20060040225A1 (en) * | 2004-07-29 | 2006-02-23 | Alstom Technology Ltd | Method for operating a furnace |
US20060046218A1 (en) * | 2004-01-12 | 2006-03-02 | Joklik Richard G | System and method for flame stabilization and control |
US7334413B2 (en) * | 2004-05-07 | 2008-02-26 | Rosemount Aerospace Inc. | Apparatus, system and method for observing combustion conditions in a gas turbine engine |
US7454892B2 (en) * | 2002-10-30 | 2008-11-25 | Georgia Tech Research Corporation | Systems and methods for detection and control of blowout precursors in combustors using acoustical and optical sensing |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1162824A (en) * | 1965-09-07 | 1969-08-27 | Honeywell Inc | Flame Failure Safety System |
EP0918152A1 (en) | 1997-11-24 | 1999-05-26 | Abb Research Ltd. | Method and apparatus for controlling thermo-acoustic vibratins in combustion chambers |
DE19928226A1 (en) | 1999-05-07 | 2001-02-01 | Abb Alstom Power Ch Ag | Process for suppressing or controlling thermoacoustic vibrations in a combustion system and combustion system for carrying out the process |
DE10333671A1 (en) * | 2003-07-24 | 2005-08-04 | Alstom Technology Ltd | Method for reducing the NOx emissions of a burner assembly comprising several burners and burner arrangement for carrying out the method |
DE102004015186A1 (en) * | 2004-03-29 | 2005-10-20 | Alstom Technology Ltd Baden | Gas turbine combustor and associated operating method |
DE102004015187A1 (en) * | 2004-03-29 | 2005-10-20 | Alstom Technology Ltd Baden | Combustion chamber for a gas turbine and associated operating method |
US7484369B2 (en) | 2004-05-07 | 2009-02-03 | Rosemount Aerospace Inc. | Apparatus for observing combustion conditions in a gas turbine engine |
-
2006
- 2006-03-30 DE DE102006015230A patent/DE102006015230A1/en not_active Withdrawn
-
2007
- 2007-01-31 EP EP07101481.5A patent/EP1840464B1/en not_active Not-in-force
- 2007-02-20 US US11/676,584 patent/US7901203B2/en not_active Expired - Fee Related
Patent Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4913647A (en) * | 1986-03-19 | 1990-04-03 | Honeywell Inc. | Air fuel ratio control |
US4934926A (en) * | 1988-03-25 | 1990-06-19 | Agency Of Industrial Science & Technology, Ministry Of International Trade & Industry | Method and apparatus for monitoring and controlling burner operating air equivalence ratio |
US5487266A (en) * | 1992-05-05 | 1996-01-30 | General Electric Company | Combustion control for producing low NOx emissions through use of flame spectroscopy |
US5249954A (en) * | 1992-07-07 | 1993-10-05 | Electric Power Research Institute, Inc. | Integrated imaging sensor/neural network controller for combustion systems |
US5522721A (en) * | 1993-10-29 | 1996-06-04 | L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude | Process for combustion in an industrial furnace |
US5544478A (en) * | 1994-11-15 | 1996-08-13 | General Electric Company | Optical sensing of combustion dynamics |
US5706643A (en) * | 1995-11-14 | 1998-01-13 | United Technologies Corporation | Active gas turbine combustion control to minimize nitrous oxide emissions |
US5755819A (en) * | 1996-05-24 | 1998-05-26 | General Electric Company | Photodiode array for analysis of multi-burner gas combustors |
US5978525A (en) * | 1996-06-24 | 1999-11-02 | General Electric Company | Fiber optic sensors for gas turbine control |
US6464489B1 (en) * | 1997-11-24 | 2002-10-15 | Alstom | Method and apparatus for controlling thermoacoustic vibrations in a combustion system |
US6468069B2 (en) * | 1999-10-25 | 2002-10-22 | Jerome H. Lemelson | Automatically optimized combustion control |
US6702571B2 (en) * | 2001-09-05 | 2004-03-09 | Gas Technology Institute | Flex-flame burner and self-optimizing combustion system |
US6742341B2 (en) * | 2002-07-16 | 2004-06-01 | Siemens Westinghouse Power Corporation | Automatic combustion control for a gas turbine |
US7454892B2 (en) * | 2002-10-30 | 2008-11-25 | Georgia Tech Research Corporation | Systems and methods for detection and control of blowout precursors in combustors using acoustical and optical sensing |
US20060046218A1 (en) * | 2004-01-12 | 2006-03-02 | Joklik Richard G | System and method for flame stabilization and control |
US20050247064A1 (en) * | 2004-02-06 | 2005-11-10 | Lieuwen Tim C | Systems and methods for detection of combustor stability margin |
US7334413B2 (en) * | 2004-05-07 | 2008-02-26 | Rosemount Aerospace Inc. | Apparatus, system and method for observing combustion conditions in a gas turbine engine |
US20060040225A1 (en) * | 2004-07-29 | 2006-02-23 | Alstom Technology Ltd | Method for operating a furnace |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2947389A1 (en) * | 2014-05-23 | 2015-11-25 | United Technologies Corporation | A gas turbine engine optical system |
US9885609B2 (en) | 2014-05-23 | 2018-02-06 | United Technologies Corporation | Gas turbine engine optical system |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
CN113915007A (en) * | 2021-11-11 | 2022-01-11 | 西安热工研究院有限公司 | Novel combustion pressure pulsation control system of gas turbine |
Also Published As
Publication number | Publication date |
---|---|
EP1840464A1 (en) | 2007-10-03 |
US7901203B2 (en) | 2011-03-08 |
EP1840464B1 (en) | 2017-06-28 |
DE102006015230A1 (en) | 2007-10-18 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7901203B2 (en) | Combustion chamber | |
US8677947B2 (en) | Boiler system | |
RU2454613C1 (en) | Multi-section boiler and control method of such boiler, which prevent exit gas thrust reversing | |
RU2008133989A (en) | FUEL COEFFICIENT MANAGEMENT IN A COMBUSTION DEVICE WITH MULTIPLE FUEL SUPPLY PIPELINES | |
US20120100493A1 (en) | Assured compliance mode of operating a combustion system | |
US20200271312A1 (en) | Boiler combustor side blockage detection system and method | |
KR20150069034A (en) | Methods and apparatus for efficient operation of an abatement system | |
CN108119895A (en) | Waste heat boiler liquid level of steam drum control system | |
CN108266714A (en) | Waste heat boiler liquid level of steam drum control method | |
JP5914147B2 (en) | Multi-can type once-through boiler unit control system | |
CN110486947A (en) | A kind of two fans gas heater | |
US10655755B2 (en) | Sensor connection structure | |
WO2014033837A1 (en) | Waste heat recovery boiler, method for controlling waste heat recovery boiler, and combined cycle power generation plant using same | |
CN109099582B (en) | Boiler system | |
JP2001132940A (en) | Exhaust gas backdraft preventer in multi-boiler system | |
JP2008223701A (en) | Control device of process steam utilizing steam turbine | |
US10533771B2 (en) | Blower assembly with compensation for vent back pressure | |
KR101038116B1 (en) | apparatus and method of furnace pressure control in regenerative reheating furnace | |
CN110953719B (en) | Control method for preventing overhigh heating water outlet temperature of gas water heater | |
WO2008138797A2 (en) | Pressure dynamics reduction within a gas turbine engine | |
CN108443710B (en) | Natural gas pressure-regulating heating system and pressure-regulating heating method | |
WO2016135494A1 (en) | A method of monitoring the usage of a boiler, a boiler and a boiler usage sensor | |
US20220341601A1 (en) | Furnace monitoring and control based on rate of flue gas temperature change | |
CN203704373U (en) | Oil or gas fired vacuum hot water boiler control system | |
CN215983244U (en) | High-temperature heat energy system and high-temperature heat energy control system |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:NI, ALEXANDER;BELLUCCI, VALTER;FLOHR, PETER;AND OTHERS;SIGNING DATES FROM 20070305 TO 20070408;REEL/FRAME:019416/0283 Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:NI, ALEXANDER;BELLUCCI, VALTER;FLOHR, PETER;AND OTHERS;REEL/FRAME:019416/0283;SIGNING DATES FROM 20070305 TO 20070408 |
|
FEPP | Fee payment procedure |
Free format text: PAYER NUMBER DE-ASSIGNED (ORIGINAL EVENT CODE: RMPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
AS | Assignment |
Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:038216/0193 Effective date: 20151102 |
|
AS | Assignment |
Owner name: ANSALDO ENERGIA SWITZERLAND AG, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC TECHNOLOGY GMBH;REEL/FRAME:041686/0884 Effective date: 20170109 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20190308 |